CN205044942U - But hybrid tilt wing aircraft - Google Patents
But hybrid tilt wing aircraft Download PDFInfo
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- CN205044942U CN205044942U CN201520700469.6U CN201520700469U CN205044942U CN 205044942 U CN205044942 U CN 205044942U CN 201520700469 U CN201520700469 U CN 201520700469U CN 205044942 U CN205044942 U CN 205044942U
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Abstract
The utility model relates to an aircraft field especially relates to a but hybrid tilt wing aircraft, the utility model discloses an electronic many rotors module and aeroengine stationary vane module combine, two movable tilting wings are in vertical position during takeoff phase, the biggest lift when becoming vertical position and can provide but hybrid tilt wing aircraft and take off, four rotors keep the stable but hybrid tilt wing aircraft that makes of fuselage steadily to rise, when rising to required highly cruising, two movable tilting wings become the horizontality, four rotors are packed up, reduce aerodynamic drag, thereby make the flight of but hybrid tilt wing aircraft safety and stability, fixed -wing aircraft and the respective advantage of many gyroplane have been exert, require lowly to the place of taking off and descending promptly, it is reliable and stable when cruising, hybrid's power mode, can be according to the power mode of actual conditions option demand during the use, the energy can be saved's effect has been reached.
Description
Technical field
The utility model relates to aircraft field, and particularly relating to a kind of hybrid power can tilt wing aircraft.
Background technology
Existing aircraft mainly comprises two kinds of fixed-wings and many rotors, wherein fix autogiro and mainly comprise two large fixed-wings, can take off vertically, vertical landing and forward flight, flight safety is stablized, but fixed wing aircraft all needs longer runway to provide the power taken off usually, takes off limited.Many autogiros provide the power taken off without the need to runway, and can aloft stagnate, but the flight of many autogiros is unstable, and safety factor is low.
Utility model content
The purpose of this utility model is the defect overcoming prior art existence, and do not limit by place when providing one to take off and land, when cruising, the hybrid power of safety and steady can tilt wing aircraft.
The technical scheme realizing the utility model object is: a kind of hybrid power can tilt wing aircraft, comprise main machine body, electronic many rotor module, aero-engine fixed-wing module, flight-control computer and empennage, flight-control computer is arranged in main machine body, empennage is arranged on the afterbody of main machine body, electronic many rotor module comprise four hydraulic actuators and four rotors, four hydraulic actuators two one group are arranged on the front-end and back-end of main machine body respectively, rotor comprises brushless motor, two leaves fold oar, carbon fiber support and rack joint bearing, two leaves fold oar and are arranged on brushless motor, brushless motor is arranged on the end of carbon fiber support, carbon fiber support is by the left and right sides being fixed on main machine body of rack joint bearing symmetry, four hydraulic actuators are connected in four carbon fiber support, four rotors launch respectively by four hydraulic actuators and pack up, aero-engine fixed-wing module comprises two movable tilting wings, wing root bearing, two aero-engine screw propellers and wing and to vert hydraulic actuator, two movable tilting wings are fixed on the middle part of main machine body by wing root bearing, two aero-engine screw propellers are arranged on two movable tilting wings respectively, the wing hydraulic actuator that verts is arranged on wing root bearing, and the wing hydraulic actuator that verts acts on wing root bearing and makes two movable tilting wings become level or plumbness.
As prioritization scheme of the present utility model, electronic many rotor module provide power by lithium cell.
As prioritization scheme of the present utility model, the end of two aero-engine screw propellers installs the fuel engines driving aero-engine screw propeller to rotate respectively.
As prioritization scheme of the present utility model, hybrid power can tilt wing aircraft also comprise control hybrid power can tilt wing aircraft flight time turn Vertical Square guide vane, Vertical Square guide vane is arranged on the top, rear of main machine body.
The utility model has positive effect: the utility model is combined by electronic many rotor module and aero-engine fixed-wing module, during takeoff phase, two movable tilting wings are in plumbness, becoming plumbness can provide hybrid power can the maximum lift of tilt wing aircraft when taking off, four rotors maintenance fuselages are stablized makes hybrid power steadily rise by tilt wing aircraft, when rising to required height and cruising, two movable tilting wings become horizontality, four rotors are packed up, reduce air resistance, thus make hybrid power can the flight of tilt wing aircraft safety and stability, the utility model has played fixed wing aircraft and many autogiros advantage separately, namely low to the site requirements taken off and land, reliable and stable when cruising, the dynamic mode of oil electricity mixing, the dynamic mode of needs can be selected according to actual conditions during use, reach the effect of saving the energy.
Accompanying drawing explanation
In order to make content of the present utility model more easily be clearly understood, below according to specific embodiment also by reference to the accompanying drawings, the utility model is described in further detail, wherein:
Fig. 1 is that hybrid power can the constructional drawing of tilt wing aircraft;
Fig. 2 is that hybrid power can the schematic diagram of tilt wing aircraft takeoff phase;
Fig. 3 is that hybrid power can the schematic diagram of tilt wing aircraft acceleration phase;
Fig. 4 is that hybrid power can the schematic diagram of tilt wing aircraft cruising phase.
Wherein, 1, main machine body, 4, flight-control computer, 5, empennage, 21, hydraulic actuator, 22, brushless motor, 23, two leaves fold oar, and 24, carbon fiber support, 25, rack joint bearing, 31, movable tilting wing, 32, wing root bearing, 33, aero-engine screw propeller, 34, wing verts hydraulic actuator, 35, fuel engines, 6, Vertical Square guide vane.
Detailed description of the invention
As shown in Figure 1, the utility model discloses a kind of hybrid power can tilt wing aircraft, comprise main machine body 1, electronic many rotor module, aero-engine fixed-wing module, flight-control computer 4 and empennage 5, wherein, flight-control computer 4 is arranged in main machine body 1, empennage 5 is arranged on the afterbody of main machine body 1, electronic many rotor module comprise four hydraulic actuators 21 and four rotors, four hydraulic actuators 21 two one group are arranged on the front-end and back-end of main machine body 1 respectively, rotor comprises brushless motor 22, two leaves fold oar 23, carbon fiber support 24 and rack joint bearing 25, two leaves fold oar 23 and are arranged on brushless motor 22, brushless motor 22 is arranged on the end of carbon fiber support 24, carbon fiber support 24 is by the left and right sides being fixed on main machine body 1 of rack joint bearing 25 symmetry, four hydraulic actuators 21 are connected in four carbon fiber support 24, four rotors launch respectively by four hydraulic actuators 21 and pack up, aero-engine fixed-wing module comprises two movable tilting wings 31, wing root bearing 32, two aero-engine screw propellers 33 and wing and to vert hydraulic actuator 34, two movable tilting wings 31 are fixed on the middle part of main machine body 1 by wing root bearing 32, two aero-engine screw propellers 33 are arranged on two movable tilting wings 31 respectively, the wing hydraulic actuator 34 that verts is arranged on wing root bearing 32, and the wing hydraulic actuator 34 that verts acts on wing root bearing 32 and makes two movable tilting wings 31 become level or plumbness.
Wherein, flight-control computer 4 control hybrid power can the state of flight of tilt wing aircraft.Rack joint bearing 25 is arranged on the below of main machine body 1, and be positioned at the below of main machine body 1 when four rotors are packed up by four hydraulic actuators 21, electronic many rotor module provide power by lithium cell, and wherein lithium cell is high-capacity lithium cell.
The end of two aero-engine screw propellers 33 installs the fuel engines 35 driving aero-engine screw propeller 33 to rotate respectively.Fuel engines 35 drives aero-engine screw propeller 33 to rotate, and offsets fuel engines 35 torsion and the thrust balancing two fuel enginess 35 makes hybrid power can tilt wing aircraft flight.
Hybrid power can tilt wing aircraft also comprise control hybrid power can tilt wing aircraft flight time turn Vertical Square guide vane 6, Vertical Square guide vane 6 is arranged on the top, rear of main machine body 1.Vertical Square guide vane 6 major control hybrid power can tilt wing aircraft turn time direction.
Fig. 2 is that hybrid power can the schematic diagram of tilt wing aircraft takeoff phase, during takeoff phase, two movable tilting wings 31 are in plumbness, becoming plumbness can provide hybrid power can the maximum lift of tilt wing aircraft when taking off, four rotors are launched by four hydraulic actuators 21, controlled by flight-control computer 4, regulate flying speed, make hybrid power steadily increase to reach required height by tilt wing aircraft.
Fig. 3 is that hybrid power can the schematic diagram of tilt wing aircraft acceleration phase, when hybrid power can tilt wing aircraft reach predetermined height time, now hybrid power can be in acceleration phase by tilt wing aircraft, the wing hydraulic actuator 34 that verts acts on wing root bearing 32 and makes two movable tilting wings 31 become horizontality simultaneously, become horizontality and can reduce air resistance in accelerator, shorten pick-up time.
Fig. 4 is that hybrid power can the schematic diagram of tilt wing aircraft cruising phase, when hybrid power can after tilt wing aircraft acceleration phase completes, now two movable tilting wings 31 are horizontality, reduce air resistance, thrust during flight is provided, in order to make hybrid power better fly by tilt wing aircraft, four rotors are packed up by four hydraulic actuators 21, hybrid power can tilt wing aircraft can the flight of steady as common fixed wing aircraft, fast speed.
Above-described specific embodiment; the purpose of this utility model, technical scheme and beneficial effect are further described; be understood that; the foregoing is only specific embodiment of the utility model; be not limited to the utility model; all within spirit of the present utility model and principle, any amendment made, equivalent replacement, improvement etc., all should be included within protection domain of the present utility model.
Claims (4)
1. a hybrid power can tilt wing aircraft, comprise main machine body (1), electronic many rotor module, aero-engine fixed-wing module, flight-control computer (4) and empennage (5), described flight-control computer (4) is arranged in main machine body (1), described empennage (5) is arranged on the afterbody of main machine body (1), it is characterized in that: electronic many rotor module comprise four hydraulic actuators (21) and four rotors, four described hydraulic actuators (21) two one group are arranged on the front-end and back-end of main machine body (1) respectively, described rotor comprises brushless motor (22), two leaves fold oar (23), carbon fiber support (24) and rack joint bearing (25), two described leaves fold oar (23) and are arranged on brushless motor (22), described brushless motor (22) is arranged on the end of carbon fiber support (24), described carbon fiber support (24) is by the left and right sides being fixed on main machine body (1) of rack joint bearing (25) symmetry, four hydraulic actuators (21) are connected on four carbon fiber support (24), four rotors launch respectively by four hydraulic actuators (21) and pack up, described aero-engine fixed-wing module comprises two movable tilting wings (31), wing root bearing (32), two aero-engine screw propellers (33) and wing vert hydraulic actuator (34), two movable tilting wings (31) are fixed on the middle part of main machine body (1) by wing root bearing (32), two aero-engine screw propellers (33) are arranged on two movable tilting wings (31) respectively, the described wing hydraulic actuator (34) that verts is arranged on wing root bearing (32), the described wing hydraulic actuator (34) that verts acts on wing root bearing (32) and makes two movable tilting wings (31) become level or plumbness.
2. a kind of hybrid power according to claim 1 can tilt wing aircraft, it is characterized in that: described electronic many rotor module provide power by lithium cell.
3. a kind of hybrid power according to claim 2 can tilt wing aircraft, it is characterized in that: the end of two aero-engine screw propellers (33) installs the fuel engines (35) driving aero-engine screw propeller (33) to rotate respectively.
4. a kind of hybrid power according to claim 3 can tilt wing aircraft, it is characterized in that: described hybrid power can tilt wing aircraft also comprise control hybrid power can tilt wing aircraft flight time turn Vertical Square guide vane (6), described Vertical Square guide vane (6) is arranged on the top, rear of main machine body (1).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520700469.6U CN205044942U (en) | 2015-09-10 | 2015-09-10 | But hybrid tilt wing aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520700469.6U CN205044942U (en) | 2015-09-10 | 2015-09-10 | But hybrid tilt wing aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN205044942U true CN205044942U (en) | 2016-02-24 |
Family
ID=55338541
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201520700469.6U Withdrawn - After Issue CN205044942U (en) | 2015-09-10 | 2015-09-10 | But hybrid tilt wing aircraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN205044942U (en) |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105173075A (en) * | 2015-09-10 | 2015-12-23 | 南京多零无人机技术有限公司 | Tiltable hybrid rotor-wing aircraft |
| CN106155085A (en) * | 2016-08-05 | 2016-11-23 | 武汉捷特航空科技有限公司 | A kind of unmanned plane assisting in flying control method, system and unmanned plane |
| CN106741906A (en) * | 2017-02-14 | 2017-05-31 | 徐志勇 | Many collapsible unmanned planes of rotor |
| US10562622B2 (en) | 2016-08-11 | 2020-02-18 | Unist (Ulsan National Institute Of Science And Technology) | Apparatus and method for controlling stability of unmanned aerial vehicle |
| US11439050B2 (en) | 2018-06-27 | 2022-09-06 | Kunshan Go-Visionox Opto-Electronics Co., Ltd. | Mark recognition devices, mark recognition methods and pseudo pressure alignment devices |
-
2015
- 2015-09-10 CN CN201520700469.6U patent/CN205044942U/en not_active Withdrawn - After Issue
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105173075A (en) * | 2015-09-10 | 2015-12-23 | 南京多零无人机技术有限公司 | Tiltable hybrid rotor-wing aircraft |
| CN106155085A (en) * | 2016-08-05 | 2016-11-23 | 武汉捷特航空科技有限公司 | A kind of unmanned plane assisting in flying control method, system and unmanned plane |
| US10562622B2 (en) | 2016-08-11 | 2020-02-18 | Unist (Ulsan National Institute Of Science And Technology) | Apparatus and method for controlling stability of unmanned aerial vehicle |
| CN106741906A (en) * | 2017-02-14 | 2017-05-31 | 徐志勇 | Many collapsible unmanned planes of rotor |
| US11439050B2 (en) | 2018-06-27 | 2022-09-06 | Kunshan Go-Visionox Opto-Electronics Co., Ltd. | Mark recognition devices, mark recognition methods and pseudo pressure alignment devices |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| AV01 | Patent right actively abandoned |
Granted publication date: 20160224 Effective date of abandoning: 20170915 |
|
| AV01 | Patent right actively abandoned |